| タイトル | Hydrocarbon-fueled scramjet combustor investigation |
| 著者（英） | Guile, R. N.; Kay, I. W.; Peschke, W. T. |
| 著者所属（英） | United Technologies Research Center |
| 発行日 | 1990-07-01 |
| 言語 | eng |
| 内容記述 | An experimental program is being conducted for developing the technology required by a hydrocarbon-fueled engine capable of operating as a scramjet in the Mach 5.6-7.0 range. A series of tests have been run to define scramjet combustor design criteria applicable to a scramjet configuration involving a pair of modular, axisymmetric combustors mounted on the lower surface of a supersonic/hypersonic missile. The airbreathing pilot combustor incorporates an external mainstream fuel injector which serves as the primary fuel injection stage for the supersonic combustor; it has been demonstrated that the pilot promotes the efficient combustion of either gaseous ethylene or preheated JP-5, when they are injected into the mainstream flow as a primary fuel. |
| NASA分類 | AIRCRAFT PROPULSION AND POWER |
| レポートNO | 90A40622
AIAA PAPER 90-2337 |
| 権利 | Copyright |
